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Mission Overview — 30 December 2002

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Mission Overview — 30 December 2002 THE VEHICLE THE SATELLITE PROTON HISTORY PROTON DESCRIPTION Lead designer was Vladimir Chelomei, who designed it TOTAL HEIGHT with the intention of creating both a powerful rocket for 58.2 m (191 ft) military payloads and a high-performance ICBM. The program was changed, and the rocket was developed GRoss LIFT-OFF exclusively for launching spacecraft. WEIGHT 705,000 kg First named UR-500, but adopted the name (1,554,000 lb) “Proton,” which also was the name of the first PROPELLANT three payloads launched. UDMH and NTO Proton launched Russian interplanetary mis- INITIAL LAUNCH sions to the Moon, Venus, Mars, and Hal- 16 July 1965 ley’s Comet. Proton-1 Spacecraft Proton launched the Salyut space sta- PAYLOAD FAIRINGS tions, the Mir core segment and both There are multiple payload fairing designs presently SATELLITE OPERATOR the Zarya (Dawn) and Zvezda (Star) mod- qualified for flight, including ules for today’s International Space Station. SES standard commercial payload www.ses.com fairings developed specifically to First commercial Proton launch, Astra 1F — meet the needs of our customers. 9 April 1996. SATELLITE MANUFACTURER BREEZE M UPPER STAGE Astrium First commercial Proton M Breeze M launch The Breeze M is powered by one pump-fed www.astrium.eads.net Mission Overview — 30 December 2002. gimbaled main engine that develops thrust of 20 kN (4,500 lbf). It is composed of a central core and PLATFORM an auxilliary propellant tank which is jettisoned in flight Eurostar E3000 following depletion. The Breeze M control system includes an on-board computer, a three-axis gyro stabilized platform, and a SEPARATED MAss navigation system. The quantity of propellant carried is dependent 6020 kg on specific mission requirements and is varied to maximize mission Experience ILS: Achieve Your Mission performance. SATELLITE MIssION LIFETIME QUALITY | PERFORMANCE | EXPERIENCE | DEDICATION PROTON BoosTER 15 Years The Proton booster is 4.1 m (13.5 ft) in diameter along its second and third stages, with a first stage diameter of 7.4 m (24.3 ft). Overall SATELLITE MIssION height of the three stages of the Proton booster is 42.3 m (138.8 ft). ASTRA 2E will carry Ku- and Ka-band payloads for the delivery of www.ilslaunch.com high-performance Direct-to-Home (DTH) and next generation HIRD TAGE T S broadband services in Europe, Middle East and Africa. Built by Powered by one RD-0213 engine, this stage develops thrust of 583 kN Astrium, Astra 2E will bring replacement and growth capacity (131,000 lbf), and a four-nozzle vernier engine that produces thrust of at 28.2° East to enhance SES’ fleet of over 50 geostationary 31 kN (7,000 lbf). Guidance, navigation, and control of the Proton M during satellites, and ensure reliable and secure connectivity to over Astra 2E operation of the first three stages is carried out by a triple redundant closed-loop 99% of the world’s population. digital avionics system mounted in the Proton’s third stage. 5th ILS Proton Launch in 2013 SECOND STAGE Of conventional cylindrical design, this stage is powered by three RD-0210 engines 82nd ILS Proton Launch Overall plus one RD-0211 engine and develops a vacuum thrust of 2.4 MN (540,000 lbf). 23rd SES Satellite Launched FIRST STAGE on Proton The first stage consists of a central tank containing the oxidizer surrounded by six out- board fuel tanks. Each fuel tank also carries one of the six RD-276 engines that provide 17th Astrium Satellite Launched on first stage power. Total first stage vacuum-rated level thrust is 11.0 MN (2,500,000 lbf). Proton The Proton and the Breeze M are built by Khrunichev State Research and Production Space Center. THE MISSION Payload Fairing 3rd Stage/Breeze M 1st Burn = 00:04:31 2nd Burn = 00:17:44 3rd Burn = 00:11:30 4th Burn = 00:05:53 5th Burn = 00:06:16 Spacecraft (PLF) Separation Ignition Shutdown Ignition Shutdown Ignition Shutdown APT Jettison Ignition Shutdown Ignition Shutdown Separation Separation 00:09:42 00:11:16 00:15:47 01:07:33 01:25:17 03:28:12 03:39:42 03:40:32 03:41:59 03:47:52 08:53:08 08:59:24 09:12:00 00:05:47 MISSION DESCRIPTION GROUND TRACK The Proton M launch vehicle, utilizing a 5-burn Breeze M 7UDQVIHU2UELW mission design, will lift off from Pad 39 at Baikonur Cosmodrome, Kazakhstan, with the Astra 2E satellite on board. The first three stages of the Proton will /LIWRII use a standard ascent profile to place the orbital unit (Breeze M upper stage and the Astra 2E satellite) into a 2nd/3rd Stage sub-orbital trajectory. From this point in the mission, the 3DUNLQJ2UELW Separation Breeze M will perform planned mission maneuvers to 00:05:27 advance the orbital unit first to a circular parking orbit, then to an intermediate orbit, followed by a transfer orbit, and finally to a geosynchronous transfer orbit. Separation of the Astra 2E satellite is scheduled to occur /DWLWXGH GHJUHHV approximately 9 hours, 12 minutes after liftoff. ,QWHUPHGLDWH2UELW st nd 1 /2 Stage /RQJLWXGH GHJUHHV Separation 00:02:00 7UDQVIHU2UELW +S NP +D NP L *HR7UDQVIHU2UELW *72 +S NP +D NP Maximum Dynamic Pressure L 00:01:02 ,QWHUPHGLDWH2UELW /9/LIWRII Command Stage 1 (100% Thrust) +S NP -00:00:00.9 +D NP L Stage 1 Ignition (40% Thrust) -00:00:01.75 *HRVWDWLRQDU\ Ignition Start Sequence 2UELW *62 -00:00:02.5 3DUNLQJ2UELW +S NP +D NP LAUNCH PAD 39 L ASCENT PROFILE PROTON ON PAD 39 FLIGHT DESIGN.
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